EP1108926B1 - Rotationsmaschine mit einer Bürstendichtung - Google Patents
Rotationsmaschine mit einer Bürstendichtung Download PDFInfo
- Publication number
- EP1108926B1 EP1108926B1 EP00311156A EP00311156A EP1108926B1 EP 1108926 B1 EP1108926 B1 EP 1108926B1 EP 00311156 A EP00311156 A EP 00311156A EP 00311156 A EP00311156 A EP 00311156A EP 1108926 B1 EP1108926 B1 EP 1108926B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- section
- rotor
- axis
- bristles
- area
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
- F16J15/3284—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings characterised by their structure; Selection of materials
- F16J15/3288—Filamentary structures, e.g. brush seals
Definitions
- the present invention relates generally to rotary machines, and more particularly to a rotary machine having a brush seal.
- Rotary machines include, without limitation, turbines for steam turbines and compressors and turbines for gas turbines.
- a steam turbine has a steam path which typically includes, in serial-flow relationship, a steam inlet, a turbine, and a steam outlet.
- a gas turbine has a gas path which typically includes, in serial-flow relationship, an air intake (or inlet), a compressor, a combustor, a turbine, and a gas outlet (or exhaust nozzle). Gas or steam leakage, either out of the gas or steam path or into the gas or steam path, from an area of higher pressure to an area of lower pressure, is generally undesirable.
- gas-path leakage in the turbine or compressor area of a gas turbine, between the rotor of the turbine or compressor and the circumferentially surrounding turbine or compressor casing will lower the efficiency of the gas turbine leading to increased fuel costs.
- steam-path leakage in the turbine area of a steam turbine, between the rotor of the turbine and the circumferentially surrounding casing will lower the efficiency of the steam turbine leading to increased fuel costs.
- Annular brush seals have been proposed for use between a rotor and a surrounding casing in gas and steam turbines.
- the annular brush seal is made up of circumferentially-arrayed brush seal segments.
- Each brush seal segment is attached to the casing and includes a back (i.e., downstream) plate, a front (i.e., upstream) plate, and bristles which are positioned between the back and front plates with the free end of generally each bristle extending beyond the edges of the back and front plates.
- the bristles typically are canted at an angle of generally forty-five degrees in the direction of rotation of the rotor, and the free ends of the bristles are close to (and may even touch) the rotor.
- the front plate (and in some designs also portions of the back plate), near the free ends of the bristles, is spaced apart from the bristles to allow room for the bristles to flex and recover during transient encounters of the free ends of the bristles with the rotor.
- Known rotary machine designs as for example in GB-A-2 258 277 include a design having a stepped rotor, a first brush seal downstream of the step, and, in one example, a second brush seal upstream of the step.
- gas flow passing the step would swirl, and some of such flow would swirl between the front plate and the bristles of the first brush seal causing bristle flutter (i.e., instability) which quickly wore the bristles and lead to premature brush seal failure.
- bristle flutter i.e., instability
- some of such flow can swirl between the front plate and the bristles of the second brush seal causing bristle flutter which quickly wears the bristles leading to premature brush seal failure.
- What is needed is a design for a rotary machine which reduces bristle flutter in a brush seal located near a stepped area of the rotor.
- a rotary machine in an embodiment of the invention, includes a rotor, a stator, a first brush seal, and a second brush seal.
- the rotor has a longitudinal axis and an outer surface.
- the outer surface includes longitudinally extending first and second sections and a third section located longitudinally between, and connected to, the first and second sections.
- the first section is disposed upstream from the second section.
- the second section has a smaller radius than the first section, and the third section has at least one area located radially between the first and second sections and facing in a direction other than perpendicular or parallel to the axis.
- the stator circumferentially surrounds the rotor.
- the first brush seal is attached to the stator, has radially-inwardly-extending first front and first back plates, and has first bristles positioned longitudinally between the first back and first front plates.
- the first front plate has a first radially inner edge and a first portion extending to the edge with the first portion longitudinally spaced apart from the first bristles.
- the first back plate is located longitudinally further from the third section of the outer surface of the rotor than is the first front plate, and the first bristles have first free ends positioned near the second section of the outer surface of the rotor.
- the second brush seal is attached to the stator, has radially-inwardly-extending second front and second back plates, and has second bristles positioned longitudinally between the second back and second front plates.
- the second front plate has a second radially inner edge and a second portion extending to the edge with the second portion longitudinally spaced apart from the second bristles.
- the second front plate is located longitudinally further upstream from the second section of the outer surface of the rotor than is the second back plate, and the second bristles have second free ends positioned near the first section of the outer surface of the rotor.
- the second portion of the second front plate at the second radially inner edge has a ledge projecting generally away from the second bristles.
- the shape of the third section of the outer surface of the rotor (which acts to smooth the radial gap between the first and second sections of the outer surface of the rotor) reduces swirl in the gas flow approaching the first brush seal. This reduces swirl between the first front plate and the first bristles which reduces bristle flutter resulting in less bristle wear and increased seal life for the first brush seal.
- the ledge of the second portion of the second front plate of the second brush seal acts to channelize gas flow reducing swirl in any turbulent gas flow found upstream near the first brush seal. This reduces swirl between the second front plate and the second bristles which reduces bristle flutter resulting in less bristle wear and increased seal life for the second brush seal.
- Figure 1 schematically shows an embodiment of the rotary machine 10 of the present invention. It is noted that only a portion of the rotary machine 10 is shown in the figure.
- the rotary machine is an aircraft gas turbine engine.
- the invention is not so limited, and the invention is applicable to other rotary machines including, without limitation, gas and steam turbines used to turn electrical generators for power utility companies.
- a rotary machine 10 includes a rotor 12, a stator 14, and a first brush seal 16.
- the rotor 12 has a longitudinally extending axis 18 and an outer surface 20.
- the outer surface 20 includes generally longitudinally extending first and second sections 22 and 24 and further includes a third section 26 disposed longitudinally between, and connected to, the first and second sections 22 and 24.
- the first section 22 is disposed upstream from the second section 24.
- the first section 22 has a generally constant first radius (measured from the longitudinal axis 18), and the second section 24 has a generally constant second radius (measured from the longitudinal axis 18) which is smaller than the first radius.
- the third section 26 has at least one area 28 disposed radially between the first and second radii and facing in a direction other than perpendicular or parallel to the axis 18.
- the stator 14 is generally coaxially aligned with the axis 18 and circumferentially surrounds, and is radially spaced apart from, the rotor 12.
- the first brush seal 16 is attached to the stator 14.
- the first brush seal 16 has radially-inwardly-extending (first) front and back plates 30 and 32 and further has a plurality of (first) bristles 34 disposed longitudinally between the back and front plates 32 and 30.
- the front plate 30 has a (first) radially inner edge 36 and further has a (first) portion 38 extending to the radially inner edge 36, with the portion 38 longitudinally spaced apart from the bristles 34.
- the back plate 32 is disposed longitudinally further downstream from the third section 26 of the outer surface 20 of the rotor 12 than is the front plate 30.
- the bristles 34 have (first) free ends 39 disposed proximate the second section 24 of the outer surface 20 of the rotor 12.
- the third section 26 is radially contained entirely inward of the first radius, and in another design, the third section 26 is radially contained entirely outward of the second radius.
- the at-least-one area 28 of the third section 26 of the outer surface 20 the rotor 12 includes a first area 40 which appears as a convex arc in an above-axis, cross-sectional view taken by a cutting plane, wherein the axis 18 (i.e., the longitudinal axis of the rotor) lies in the cutting plane.
- the convex arc has a first end 42 connected to the first section 22 of the outer surface 20 of the rotor 12 and a second end 44 disposed closer to the axis 18 than is the first end 42 of the convex arc.
- the at-least-one area 28 of the third section 26 of the outer surface 20 of the rotor 12 includes a second area 46 which appears as a concave arc in the previously-described above-axis, cross-sectional view.
- the concave arc has a first end 48 connected to the second end 44 of the convex arc and further has a second end 50 connected to the second section 24 of the outer surface 20 of the rotor 12.
- the at-least-one area 28 of the third section 26 of the outer surface 20 of the rotor 12 includes a second area 46 which appears as a concave arc in the previously-described above-axis, cross-sectional view.
- the concave arc has first and second ends 48 and 50 with the first end 48 disposed further from the axis 18 (i.e., the longitudinal axis of the rotor) than is the second end 50 and with the second end 50 connected to the second section 24 of the outer surface 20 of the rotor 12.
- the convex and/or concave shape of the third section 26 of the outer surface 20 of the rotor 12 reduces swirl in the gas flow approaching the first brush seal 16. This reduces swirl between the front plate 30 and the bristles 34 which reduces bristle flutter resulting in less bristle wear and increased seal life for the first brush seal 16.
- the front plate 30 has a generally planar front face 52 oriented generally perpendicular to the axis 18 and facing away from the bristles 34.
- the front plate 30 also has a generally planar back face 54 oriented generally perpendicular to the axis 18 and facing towards the bristles 34. It is noted that the front face 52 faces upstream towards a higher pressure area 56 and that the back face 54 faces downstream towards a lower pressure area 58 with the direction of gas flow being from the higher pressure area 56 to the lower pressure area 58.
- the radially inner edge 36 of the front plate 30 connects the front and back faces 52 and 54.
- the radially inner edge 36 has a convex surface portion 60 extending from the front face 52 longitudinally towards (but not necessarily reaching) the back face 54 and radially inward toward the axis 18. It is noted that the convex surface portion 60 further reduces swirl in the gas flow approaching the first brush seal 16.
- FIG. 2 A different embodiment of the rotary machine 110 of the invention is shown in Figure 2.
- the rotary machine 110 of Figure 2 is seen to be almost identical with the previously-described embodiment of the rotary machine 10 of Figure 1.
- the one difference, as seen in Figure 2, is that the third section 126 of the outer surface 120 of the rotor 112 has a different shape and appears as a straight line in an above-axis, cross-sectional view taken by a cutting plane, wherein the longitudinal axis 118 of the rotor 112 lies in the cutting plane, and wherein the straight line has a first end 142 connected to the first section 122 of the outer surface 120 of the rotor 112 and has a second end 144 disposed closer to the axis 118 than is the first end 142.
- a rotary machine 10 includes the rotor 12, the stator 14, and the first brush seal 16 as previously described in the first expression of the embodiment of the invention shown in Figure 1.
- the previously-described front plate 30, back plate 32, bristles 34, radially inner edge 36, portion 38, and free ends 39 of the first brush seal 16 are herein denominated as first front plate 30, first back plate 32, first bristles 34, first radially inner edge 36, first portion 38, and first free ends 39 in the second expression of the embodiment of the invention shown in Figure 1.
- the rotary machine 10 additionally includes a second brush seal 62 which is attached to the stator 14.
- the second brush seal 62 has radially-inwardly-extending second front and back plates 64 and 66 and further has a plurality of second bristles 68 disposed longitudinally between the second back and front plates 66 and 64.
- the second front plate 64 has a second radially inner edge 70 and further has a second portion 72 extending to the second radially edge 70, with the second portion 72 longitudinally spaced apart from the second bristles 68.
- the second front plate 64 is disposed longitudinally further upstream from the second section 24 of the outer surface 20 of the rotor 12 than is the second back plate 66.
- the second bristles 68 have second free ends 73 disposed proximate the first section 22 of the outer surface 20 of the rotor 12.
- the second portion 72 of the second front plate 64, at the second radially inner edge 70 of the second front plate 64 has a ledge 74 projecting generally away from the second bristles 68.
- the second back plate 66 at least partially longitudinally overlaps the third section 28 of the outer surface 20 of the rotor 12.
- the second portion 72 of the second front plate 64 has a thickness along a direction parallel to the axis 18, wherein the thickness of the ledge 74 of the second portion 72 of the second front plate 64 is greater than twice the thickness (along the same previously-described direction) of any other part of the second portion 72 of the second front plate 64.
- a longer ledge 74 will channelize a turbulent gas flow reducing unwanted bristle flutter in the second bristles 68 of the second brush seal 62.
- the previously-described different embodiment of the rotary machine 110 shown in Figure 2 additionally includes a second brush seal 162 generally identical to the second brush seal 62 above-described in the second expression of the embodiment of the invention shown in Figure 1.
- the first (and second) brush seal is an annular seal defined by an array of circumferentially-arrayed annular brush seal segments, wherein a brush seal segment has only one front plate which is a manually-rigid front plate.
- a brush seal segment has only one front plate which is a manually-rigid front plate.
- manually-rigid is meant that the front plate cannot be flexed by hand by an adult person of average strength.
- a single, rigid front plate is less prone to unwanted flutter in a turbulent gas flow and is less susceptible to damage during shipping and installation and during maintenance of nearby turbine components.
- the portion of the front plate (which also can include the ledge of the second brush seal) includes through holes, wherein subflow through the through holes purges the space between the front plate and the bristles of unwanted swirl from the main flow, such purging also helping to decrease bristle flutter.
- a brush seal segment has several manually-flexible damper plates having through holes and being in contact with the front-most bristles.
- the damper plates replace, or are in addition to, the first and/or second portions 38 and 72 of the first and second front plates 30 and 64.
- the bristles are each canted at a generally-identical angle with respect to a corresponding radius line extending outward (from the axis) to each of the bristles. Such bristle canting is not visible from the views shown in the figures. In one example, the angle of the bristles is generally forty-five degrees.
- the back plate and the front plate each are of monolithic construction and consist essentially of metal or metal alloy such as, but not limited to, stainless steel.
- the bristles typically consist essentially of metal-wire or ceramic-wire bristles such as, but not limited to, cobalt-based-alloy wire bristles.
- metal-wire bristles are welded to the front and back plates.
- the brush seals are attached to the stator by engagement of the brush seal segments with a slot the stator as shown in the figures.
- the bristles have been described as being disposed proximate (and in one application disposed as to just touch) the rotor.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Sealing Devices (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Claims (10)
- Drehmaschine (10 und 11) enthaltend:a) einen Rotor (12 und 112) mit einer longitudinal verlaufenden Achse (18 und 118) und einer äusseren Oberfläche (20 und 120), wobei die äussere Oberfläche im allgemeinen longitudinal verlaufende erste und zweite Abschnitte (22 & 122 und 24) und einen dritten Abschnitt (26 und 126) aufweist, der longitudinal zwischen und mit den ersten und zweiten Abschnitten verbunden ist, wobei der erste Abschnitt stromaufwärts von dem zweiten Abschnitt angeordnet ist, wobei der erste Abschnitt einen im allgemeinen konstanten ersten Radius hat und der zweite Abschnitt einen im allgemeinen konstanten zweiten Radius hat, der kleiner als der erste Radius ist, und wobei der dritte Abschnitt wenigstens eine Fläche (28) hat, die radial zwischen den ersten und zweiten Radien angeordnet ist und in einer anderen Richtung als senkrecht oder parallel zur Achse gerichtet ist,b) einen Stator (14), der im allgemeinen koaxial mit der Achse ausgerichtet ist und den Rotor in Umfangsrichtung umgibt und radial im Abstand davon angeordnet ist,c) eine erste Bürstendichtung (16), die an dem Stator befestigt ist, radial nach innen verlaufende erste Vorder- und Rückplatten (30 und 32) aufweist und mehrere erste Borsten (34) aufweist, die longitudinal zwischen den ersten Vorder- und Rückplatten angeordnet sind, wobei die erste Frontplatte (30) einen ersten radial inneren Rand (36) und einen ersten Abschnitt (38) aufweist, der sich zu dem ersten radial inneren Rand erstreckt, wobei der erste Abschnitt longitudinal im Abstand von den ersten Borsten angeordnet ist, wobei die erste Rückplatte longitudinal weiter stromabwärts von dem dritten Abschnitt der äusseren Oberfläche des Rotors angeordnet ist als die erste Frontplatte, und wobei die ersten Borsten freie Enden haben, die nahe dem zweiten Abschnitt der äusseren Oberfläche des Rotors angeordnet sind, undd) eine zweite Bürstendichtung (62), die an dem Stator befestigt ist, radial nach innen verlaufende zweite Vorder- und Rückplatten (64 und 66) aufweist und mehrere zweite Borsten (68) aufweist, die longitudinal zwischen den zweiten Vorder- und Rückplatten angeordnet sind, dadurch gekennzeichnet, daß die zweite Frontplatte (64) einen zweiten radial inneren Rand (70) und einen zweiten Abschnitt (72) aufweist, der sich zu dem zweiten radial inneren Rand erstreckt, wobei der zweite Abschnitt longitudinal im Abstand von den zweiten Borsten angeordnet ist, wobei die zweite Frontplatte longitudinal weiter stromaufwärts von dem zweiten Abschnitt der äusseren Oberfläche des Rotors angeordnet ist als die zweite Rückplatte, wobei die zweiten Borsten freie Enden (73) haben, die nahe dem ersten Abschnitt der äusseren Oberfläche des Rotors angeordnet sind, und wobei der zweite Abschnitt von der zweiten Frontplatte an dem zweiten radial inneren Rand einen Absatz (74) hat, der im allgemeinen von den zweiten Borsten weg vorsteht.
- Drehmaschine nach Anspruch 1, wobei die zweite Rückplatte den dritten Abschnitt der äusseren Rotoroberfläche wenigstens teilweise überlappt.
- Drehmaschine nach Anspruch 1, wobei der zweite Abschnitt entlang einer Richtung parallel zur Achse eine Dicke hat und wobei die Dicke des Absatzes von dem zweiten Abschnitt der zweiten Frontplatte grösser als die doppelte Dicke von jedem anderen Abschnitt der zweiten Frontplatte ist.
- Drehmaschine nach Anspruch 1, wobei die wenigstens eine Fläche des dritten Abschnittes (126) der äusseren Rotoroberfläche als eine gerade Linie in einer über der Achse liegenden Querschnittsansicht erscheint, die durch eine Schnittebene gemacht ist, wobei die Längsachse in der Schnittebene liegt, und wobei die gerade Linie ein erstes Ende (142), das mit dem ersten Abschnitt der äusseren Rotorfläche verbunden ist, und ein zweites Ende (144) aufweist, das näher an der Achse als das erste Ende angeordnet ist.
- Drehmaschine nach Anspruch 1, wobei die wenigstens eine Fläche des dritten Abschnittes (26) der äusseren Rotoroberfläche eine erste Fläche (40) aufweist, die als ein konvexer Bogen in einer über der Achse liegenden Querschnittsansicht erscheint, die durch eine Schnittebene gemacht ist, wobei die Längsachse in der Schnittebene liegt, und wobei der konvexe Bogen ein erstes Ende (42), das mit dem ersten Abschnitt der äusseren Rotorfläche verbunden ist, und ein zweites Ende (44) aufweist, das näher an der Achse als das erste Ende von dem konvexen Bogen angeordnet ist.
- Drehmaschine nach Anspruch 5, wobei die wenigstens eine Fläche von dem dritten Abschnitt der äusseren Rotoroberfläche eine zweite Fläche (46) aufweist, die als ein konkaver Bogen in der über der Achse liegenden Querschnittsansicht erscheint, und wobei der konkave Bogen ein erstes Ende (48), das mit dem zweiten Ende von dem konvexen Bogen verbunden ist, und ein zweites Ende (50) aufweist, das mit dem zweiten Abschnitt von der äusseren Rotoroberfläche verbunden ist.
- Drehmaschine nach Anspruch 1, wobei die wenigstens eine Fläche von dem dritten Abschnitt der äusseren Rotoroberfläche eine zweite Fläche aufweist, die als ein konkaver Bogen in der über der Achse liegenden Querschnittsansicht erscheint, die durch eine Schnittebene gemacht ist, wobei die Längsachse in der Schnittebene liegt, und wobei der konkave Bogen erste und zweite Enden hat, wobei das erste Ende weiter entfernt von der Achse angeordnet ist als das zweite Ende und wobei das zweite Ende mit dem zweiten Abschnitt von der äusseren Rotoroberfläche verbunden ist.
- Drehmaschine nach Anspruch 1, wobei die Frontplatte eine im allgemeinen ebene Frontfläche (52), die im allgemeinen senkrecht zur Achse orientiert und von den Borsten weg gerichtet ist, und eine im allgemeinen ebene Rückfläche (54) hat, die im allgemeinen senkrecht zur Achse orientiert und auf die Borsten gerichtet ist, wobei der radial innere Rand der Frontplatte mit den Vorder- und Rückflächen verbunden ist und wobei der radial innere Rand einen konvexen Oberflächenabschnitt (60) hat, der sich von der Frontfläche longitudinal zur Rückfläche und radial nach innen zur Achse erstreckt.
- Drehmaschine nach Anspruch 8, wobei die wenigstens eine Fläche von dem dritten Abschnitt er äusseren Rotoroberfläche eine erste Fläche aufweist, die als ein konvexer Bogen in einer über der Achse liegenden Querschnittsansicht erscheint, die durch eine Schnittebene gemacht ist, wobei die Längsachse in der Schnittebene liegt, und wobei der konvexe Bogen ein erstes Ende, das mit dem ersten Abschnitt der äusseren Rotorfläche verbunden ist, und ein zweites Ende aufweist, das näher an der Achse als das erste Ende von dem konvexen Bogen angeordnet ist.
- Drehmaschine nach Anspruch 9, wobei die wenigstens eine Fläche von dem dritten Abschnitt der äusseren Rotoroberfläche eine zweite Fläche aufweist, die als ein konkaver Bogen in der über der Achse liegenden Querschnittsansicht erscheint, und wobei der konkave Bogen ein erstes Ende, das mit dem zweiten Ende von dem konvexen Bogen verbunden ist, und ein zweites Ende aufweist, das mit dem zweiten Abschnitt von der äusseren Rotoroberfläche verbunden ist.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US461895 | 1983-01-28 | ||
US09/461,895 US6302646B1 (en) | 1999-12-15 | 1999-12-15 | Rotary machine containing a brush seal |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1108926A1 EP1108926A1 (de) | 2001-06-20 |
EP1108926B1 true EP1108926B1 (de) | 2004-12-01 |
Family
ID=23834380
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00311156A Expired - Lifetime EP1108926B1 (de) | 1999-12-15 | 2000-12-12 | Rotationsmaschine mit einer Bürstendichtung |
Country Status (4)
Country | Link |
---|---|
US (1) | US6302646B1 (de) |
EP (1) | EP1108926B1 (de) |
JP (1) | JP2001295609A (de) |
DE (1) | DE60016366T2 (de) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6910858B2 (en) * | 2002-12-26 | 2005-06-28 | United Technologies Corporation | Seal |
EP1707856A1 (de) * | 2005-04-01 | 2006-10-04 | Cross Manufacturing Company (1938) Limited | Bürstendichtungen |
GB2452967A (en) * | 2007-09-21 | 2009-03-25 | Rolls Royce Plc | A seal and rotor arrangement including a rotor section and a circumferential movable seal around the rotor section |
US8146922B2 (en) * | 2008-06-25 | 2012-04-03 | Dresser-Rand Company | Shaft isolation seal |
DE102011080834A1 (de) * | 2011-08-11 | 2013-02-14 | Siemens Aktiengesellschaft | Bürstendichtung |
JP6022979B2 (ja) * | 2013-03-27 | 2016-11-09 | 荏原冷熱システム株式会社 | ターボ冷凍機の圧縮機用電動機 |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2250789B (en) * | 1990-12-12 | 1994-03-30 | Rolls Royce Plc | Brush seal arrangement |
GB2258277B (en) * | 1991-07-29 | 1995-02-22 | Europ Gas Turbines Ltd | Brush seals |
US5335920A (en) * | 1992-08-20 | 1994-08-09 | General Electric Company | Brush seal |
US5474306A (en) * | 1992-11-19 | 1995-12-12 | General Electric Co. | Woven seal and hybrid cloth-brush seals for turbine applications |
US5400952A (en) * | 1993-10-25 | 1995-03-28 | General Electric Company | Method and apparatus for damping a brush seal |
US5961280A (en) * | 1997-09-12 | 1999-10-05 | General Elecgtric Company | Anti-hysteresis brush seal |
US5971400A (en) | 1998-08-10 | 1999-10-26 | General Electric Company | Seal assembly and rotary machine containing such seal assembly |
US6168377B1 (en) * | 1999-01-27 | 2001-01-02 | General Electric Co. | Method and apparatus for eliminating thermal bowing of steam turbine rotors |
US6139019A (en) * | 1999-03-24 | 2000-10-31 | General Electric Company | Seal assembly and rotary machine containing such seal |
-
1999
- 1999-12-15 US US09/461,895 patent/US6302646B1/en not_active Expired - Fee Related
-
2000
- 2000-12-12 DE DE60016366T patent/DE60016366T2/de not_active Expired - Fee Related
- 2000-12-12 EP EP00311156A patent/EP1108926B1/de not_active Expired - Lifetime
- 2000-12-14 JP JP2000379561A patent/JP2001295609A/ja not_active Withdrawn
Also Published As
Publication number | Publication date |
---|---|
DE60016366T2 (de) | 2005-10-27 |
EP1108926A1 (de) | 2001-06-20 |
DE60016366D1 (de) | 2005-01-05 |
US6302646B1 (en) | 2001-10-16 |
JP2001295609A (ja) | 2001-10-26 |
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